Subsonic flight investigation of methods to improve the damping of lateral oscillations by means of a viscous damper in the rudder system in conjunction with adjusted hinge-moment parameters

Harold L. Crane, George J. Hurt, Jr., John M. Elliott
naca-tn-4193
Jan 1958


A flight investigation at subsonic speeds of a method to improve the damping of lateral oscillations by means of a viscous damping cylinder used in the rudder system in conjunction with adjusted hinge-moment parameters has been conducted. The damping device has been applied to a modern fighter-type jet-powered airplane. The rudder was made to float with the relative wind by the addition of trailing-edge strips. In order to amplify the floating tendency (by reducing the restoring moment), a highly geared balancing tab was incorporated. Lag of the motion of the free rudder with respect to the yawing of the airplane was introduced by means of a small viscous damping cylinder linked to the rudder.

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